Carrier Landing Flight Path Angle Control via Higher-Order Sliding Mode

The accuracy of flight path angle is significant in carrier landing, thus the control of flight path angle is studied in this paper. A flight control system is designed via higher-order sliding mode which is bounded, continuously time-dependent, and provides higher accuracy than standard sliding mode. The robust exact differentiator is used to calculate the higher-order derivatives of sliding mode manifold. Based on aforementioned system, the automatic power compensate system is designed via PID controller. The simulation results are presented.